Aero-engine turbine guide blade repairing device and repairing method

The invention provides an aero-engine turbine guide blade repairing device and method, relates to the technical field of engines, and aims at solving the problem that in the repairing process of an existing turbine blade, due to laser cladding, thermal stress concentration occurs on a repaired part. The aero-engine turbine guide vane repairing device comprises an operation box, an inert gas storage tank, a positioning clamp, a mechanical arm, a laser cladding head, a plurality of auxiliary plates and a heat dissipation assembly. An air inlet and an air outlet are formed in the operation box; the inert gas storage tank is communicated with the gas inlet; the positioning clamp is mounted in the operation box; the mechanical arm is mounted in the operation box; the laser cladding head is mounted on the mechanical arm; each auxiliary plate is provided with a positioning shaft matched with a flow guide hole in a turbine blade, and the auxiliary plates are sequentially arranged and installed to form an auxiliary su